Mission and system optimization of nuclear electric propulsion vehicles for lunar and Mars missions

Gilland, James H.

The detailed mission and system optimization of low thrust electric propulsion missions is a complex, iterative process involving interaction between orbital mechanics and system performance. Through the use of appropriate approximations, initial system optimization and analysis can be performed for a range of missions. The intent of these calculations is to provide system and mission designers with simple methods to assess system design without requiring access or detailed knowledge of numerical calculus of variations optimizations codes and methods. Approximations for the mission/system optimization of Earth orbital transfer and Mars mission have been derived. Analyses include the variation of thruster efficiency with specific impulse. Optimum specific impulse, payload fraction, and power/payload ratios are calculated. The accuracy of these methods is tested and found to be reasonable for initial scoping studies. Results of optimization for Space Exploration Initiative lunar cargo and Mars missions are presented for a range of power system and thruster options.

Document ID

19920005906

Acquisition Source

Legacy CDMS

Document Type

Conference Paper

Authors

Date Acquired

September 6, 2013

Publication Date

December 1, 1991

Subject Category

Report/Patent Number

Meeting Information

Meeting: International Electric Propulsion Conference

Location: Viareggio

Country: Italy

Start Date: October 14, 1991

End Date: October 17, 1991

Sponsors: DGLR, AIAA, AIDAA, JSASS

Accession Number

92N15124

Funding Number(s)

Distribution Limits

Public

Work of the US Gov. Public Use Permitted.

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